Critical aerospace parts require damage tolerance analysis to determine the inspection intervals in-service. Such analyses, based on linear fracture mechanics, require that the fatigue crack growth (FCG) rate relation to the stress intensity factor range is applicable independent of geometry and stress. FCG rates for laser powder bed fusion Ti6Al4V material for conventional compact tension (CT) specimens have therefore been compared to FCG rates for specimens with a crack configuration more technically relevant from an industrial and engineering perspective. The FCG rates corresponded very well and data obtained with CT-specimens can therefore be considered relevant for general damage tolerance predictions.

关键的航空航天部件需要进行损伤容限分析，以确定使用中的检查间隔。这种基于线性断裂力学的分析要求疲劳裂纹扩展 (FCG) 速率与应力强度因子范围的关系适用，而与几何形状和应力无关。因此，从工业和工程的角度来看，激光粉末床熔合 Ti6Al4V 材料的 FCG 速率与用于裂纹配置的试样的 FCG 速率在技术上更相关。FCG 率对应得非常好，因此可以认为使用 CT 样本获得的数据与一般的损伤容限预测相关。